Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Morelli, Myles; Bellosta, Tommaso; Guardone, Alberto

doi:10.1016/j.cam.2020.113340

Cited by 12 publications

(8 citation statements)

References 31 publications

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“…Hence, if a certain CFD code supports the moving meshes, the required changes to the code can be minimized. 19 The ALE formulation is implemented already in HiSA solver; hence, this point is valid in our case.…”

Section: Governing Equationsmentioning

confidence: 99%

“…The relative velocity formulation is very common in the turbomachinery CFD community. 21,22 On the other hand, and since the time of introducing the absolute formulation in the pioneer work of Holmes and Tong, 33 the absolute velocity formulation became widely favored in the rotor/propeller applications [15][16][17][18][19][20]26,31 due to the following reasons:…”

Section: Governing Equationsmentioning

confidence: 99%

“…On the other hand, and for some applications, the flow fields can be solved in a noninertial reference frame without moving/deforming the mesh, for instance, evaluating the aerodynamic coefficients derivatives 15,16 or solving the flow fields for a helicopter in forward flight conditions. 17 Solving the flow fields in a non-inertial reference frame can be very advantageous for certain problems; for example, an isolated rotor/propeller [18][19][20] or a compressor blade 21,22 which rotates in a fixed rotational velocity while the free-stream velocity is parallel to the rotating axis, in such cases the problem can be treated as a steady-state problem. In this way, the complexity of the transient analyses can also be avoided, and a much faster solution can be obtained.…”

Section: Introductionmentioning

confidence: 99%

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Development of a steady-state computational fluid dynamics solver for transonic rotorcraft flows

Abuhanieh

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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The capability for solving compressible fluid flows in the rotating frame of reference is added to an existed open-source CFD solver, namely, HiSA solver. The new implementation is explained and validated using the experimental data of the Sikorsky S-76 rotor. A comparison is presented between the moving mesh results obtained from the original HiSA code and the single rotating frame results achieved through the new implementation. The comparison includes an analysis of torque and thrust values, as well as computational costs. The results imply that, for evaluating the performance of an isolated rotor or for shape optimization purposes at the transonic regime, the single rotating frame method, like the one introduced in the current work, can provide accurate results within an acceptable computational budget. Furthermore, the results show that, at least 25 revolutions are required for the transient analysis to reach an acceptable steady-state converged solution like the one obtained by the single rotating frame method.

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Section: Governing Equationsmentioning

confidence: 99%

Section: Governing Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Development of a steady-state computational fluid dynamics solver for transonic rotorcraft flows

Abuhanieh

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The application towards its use for the simulation of rotorcraft flows has recently been highlighted by Ref. [17].…”

Section: A Aerodynamic Analysismentioning

confidence: 99%

Assessment of the PoliMIce toolkit from the 1st AIAA Ice Prediction Workshop

Morelli

Bellosta

Donizetti

et al. 2022

AIAA AVIATION 2022 Forum

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This paper presents the Politecnico di Milano Icing Research Group's contribution to the 1 st AIAA Ice Prediction Workshop. A collection of two-and three-dimensional test cases to predict the collection efficiency and ice accretion are simulated using the PoliMIce ice accretion software suite. Test cases include the prediction of the collection efficiency on a three-elementairfoil and on a full-scale horizontal swept tail plane. Additionally, test cases for the simulation of ice shapes on a NACA23012 airfoil and on swept wings with varying degrees of sweep angle are assessed. The numerical predictions are evaluated and compared to high quality experimental measurements taken from the NASA Glenn Icing Research Tunnel. In general the numerical predictions compare favourably with the experimental measurements. Key droplet impingement characteristics including the collection efficiency peak and impingement limits are captured. Meanwhile distinctive ice features of rime and glaze ice regimes are depicted in the simulations. However, there remains scope for further improvement of models as highlighted by the more challenging test cases such as the three-element-airfoil and the test cases which produce glaze ice shapes with large horns.

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“…One potential solution for narrowing this design space is to apply computational fluid dynamics (CFD). Numerous solvers (mStrand (Lakshminarayan et al, 2017), SU2 (Morelli et al, 2021), OpenFoam (Nuernberg and Tao, 2018), etc.) have been developed to help streamline the process of CFD simulation of rotors.…”

Section: Introductionmentioning

confidence: 99%

A Data-Driven Reduced Order Model for Rotor Optimization

Peters

Silva²,

Ekaterinaris³

2022

Preprint

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Abstract. For rotor design applications, such as wind turbine rotor or Urban Air Mobility (UAM) rotorcraft and flying car design, there is a significant challenge in quickly and accurately modeling rotors operating in complex turbulent flow fields. One potential path for deriving high-fidelity but low-cost rotor performance predictions is available through the application of data-driven surrogate modeling. In this study, an initial investigation is undertaken to apply a proper orthogonal decomposition (POD) based reduced order model (ROM) for predicting rotor distributed loads. The POD ROM was derived based on computational fluid dynamics (CFD) results and utilized to produce distributed pressure predictions on rotor blades subjected to topology change due to variations in twist and taper ratio. Rotor twist, θ, was varied between 0°, 10°, 20°, and 30° while taper ratio, λ, was varied as 1.0, 0.9, 0.8, and 0.7. For a demonstration of the approach, all rotors consisted of a single blade. The POD ROM was validated for three operation cases; a high pitch or a high thrust rotor in hover, a low pitch or a low thrust rotor in hover, and a rotor in forward flight at a low speed resembling wind turbine operation with wind shear. Results showed highly accurate distributed load predictions could be achieved and the resulting surrogate model can predict loads at a minimal computational cost. The computational cost for the hovering blade surface pressure prediction was reduced from 12 hours on 440 cores required for CFD to a fraction of a second on a single core required for POD. For rotor in forward flight cost was reduced from 20 hours on 440 cores to less than a second on a single core. The POD ROM was used to undergo a design optimization of the rotor such that figure of merit was maximized for hovering rotor cases and the lift to drag effective ratio was maximized in forward flight.

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Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Cited by 12 publications

References 31 publications

Development of a steady-state computational fluid dynamics solver for transonic rotorcraft flows

Development of a steady-state computational fluid dynamics solver for transonic rotorcraft flows

Assessment of the PoliMIce toolkit from the 1st AIAA Ice Prediction Workshop

A Data-Driven Reduced Order Model for Rotor Optimization

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